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第5回観測ロケットシンポジウム(2023年2月28日-3月1日. オンライン開催), 5th Sounding Rocket Symposium(February 28-March 1, 2023. Online Meeting), 著者人数: 21名, 資料番号: SA6000185021, レポート番号: Ⅲ-6

第5回ハイブリッドロケットシンポジウム(2023年2月14日. オンライン開催), 5th Hybrid Rocket Symposium(February 14, 2023. Online Meeting), 資料番号: SA6000186009, HR-2022-09

令和4年度宇宙輸送シンポジウム（2023年1月12日-13日. 宇宙航空研究開発機構宇宙科学研究所（JAXA)(ISAS)) , 相模原市, 神奈川県, Space Transportation Symposium FY2022 (January 12-13, 2023. Institute of Space and Astronautical Science, Japan Aerospace Exploration Agency (JAXA)(ISAS)), Sagamihara, Kanagawa Japan, In this paper, describe a method of prediction for gas generator throttled combustion tests. In addition to the conventional method, the injector Cd was set small based on past test results. As a result, the LOX flow rate error at 70% throttle was improved from 10% to 1.3%. In addition, for flight operation, the propellant orifice diameter was examined for the feed-line resistance of the control valves., 資料番号: SA6000184027, STCP-2022-027

令和4年度宇宙輸送シンポジウム（2023年1月12日-13日. 宇宙航空研究開発機構宇宙科学研究所（JAXA)(ISAS)) , 相模原市, 神奈川県, Space Transportation Symposium FY2022 (January 12-13, 2023. Institute of Space and Astronautical Science, Japan Aerospace Exploration Agency (JAXA)(ISAS)), Sagamihara, Kanagawa Japan, Muroran Institute of Technology is conducting research and development of a Gas Generator Cycle Air Turbo Ramjet (GG-ATR) Engine as a propulsion system for small unmanned supersonic aircraft. A temperature deviation exists inside the combustion chamber of the gas generator installed in this engine. Therefore, we installed elbows, which are known to be effective in improving temperature distribution to confirm the temperature uniformity effect of the elbows. As a result, it was confirmed that the elbow improved the combustion gas temperature by 630K., 資料番号: SA6000184028, STCP-2022-028

第4回観測ロケットシンポジウム（2022年3月14-15日. ハイブリッド開催（JAXA相模原キャンパス& オンライン）), 4th Sounding Rocket Symposium(March 14-15, 2022. Hybrid(in-person & online) Conference (Institute of Space and Astronautical Science, Japan Aerospace Exploration Agency (JAXA)(ISAS)), Sagamihara, Kanagawa Japan, 著者人数: 22名, 資料番号: SA6000175011, レポート番号: Ⅱ-6

第4回ハイブリッドロケットシンポジウム(2022年2月14日. オンライン開催), 4th Hybrid Rocket Symposium(February 14, 2022. Online Meeting), 資料番号: SA6000171015, HR-2021-15

第4回ハイブリッドロケットシンポジウム(2022年2月14日. オンライン開催), 4th Hybrid Rocket Symposium(February 14, 2022. Online Meeting), 資料番号: SA6000171010, HR-2021-10

令和3年度宇宙輸送シンポジウム（2022年1月13日-14日. オンライン開催), Space Transportation Symposium FY2021 (January 13-14, 2022. Online Meeting), 著者人数: 16名, 資料番号: SA6000173015, STCP-2021-015

令和3年度宇宙輸送シンポジウム（2022年1月13日-14日. オンライン開催), Space Transportation Symposium FY2021 (January 13-14, 2022. Online Meeting), 資料番号: SA6000173017, STCP-2021-017

第3回観測ロケットシンポジウム（2021年3月24-25日. オンライン開催), 3rd Sounding Rocket Symposium (March 24-25, 2021. Online Meeting), 著者人数: 19名PDF再処理の為、2023年3月17日に差替, 資料番号: SA6000162013, レポート番号: Ⅲ-6

第3回観測ロケットシンポジウム（2021年3月24-25日. オンライン開催), 3rd Sounding Rocket Symposium (March 24-25, 2021. Online Meeting), 著者人数: 21名PDF再処理の為、2023年3月17日に差替, 資料番号: SA6000162001, レポート番号: Ⅰ-1

令和二年度宇宙輸送シンポジウム（2021年1月14日-15日. オンライン開催), Space Transportation Symposium FY2020 (January 14-15, 2021. Online Meeting), PDF再処理の為、2023年2月27日に差替, 資料番号: SA6000160007, レポート番号: STCP-2020-007

令和二年度宇宙輸送シンポジウム（2021年1月14日-15日. オンライン開催), Space Transportation Symposium FY2020 (January 14-15, 2021. Online Meeting), 著者人数: 21名PDF再処理の為、2023年2月27日に差替, 資料番号: SA6000160027, レポート番号: STCP-2020-027

令和元年度宇宙輸送シンポジウム（2020年1月16日-17日. 宇宙航空研究開発機構宇宙科学研究所（JAXA)(ISAS)）, 相模原市, 神奈川県, Space Transportation Symposium FY2019 (January 16-17, 2020. Institute of Space and Astronautical Science, Japan Aerospace Exploration Agency (JAXA)(ISAS)), Sagamihara, Kanagawa Japan, 資料番号: SA6000147036, レポート番号: STCP-2019-036

第2回観測ロケットシンポジウム（2019年8月5日-6日. 宇宙航空研究開発機構宇宙科学研究所（JAXA)(ISAS)）, 相模原市, 神奈川県, 2nd Sounding Rocket Symposium (August 5-6, 2019. Institute of Space and Astronautical Science, Japan Aerospace Exploration Agency (JAXA)(ISAS)), Sagamihara, Kanagawa Japan, 著者人数: 26名, 資料番号: SA6000142023, レポート番号: Ⅶ-2

第2回観測ロケットシンポジウム（2019年8月5日-6日. 宇宙航空研究開発機構宇宙科学研究所（JAXA)(ISAS)）, 相模原市, 神奈川県, 2nd Sounding Rocket Symposium (August 5-6, 2019. Institute of Space and Astronautical Science, Japan Aerospace Exploration Agency (JAXA)(ISAS)), Sagamihara, Kanagawa Japan, 著者人数: 17名, 設計製造協力: NETS, 山本機械設計, 資料番号: SA6000142024, レポート番号: Ⅷ-1

第2回ハイブリッドロケットシンポジウム（2019年7月11日-12日. 宇宙航空研究開発機構宇宙科学研究所（JAXA)(ISAS)）, 相模原市, 神奈川県, 2nd Hybrid Rocket Symposium (July 11-12, 2019. Institute of Space and Astronautical Science, Japan Aerospace Exploration Agency (JAXA)(ISAS)), Sagamihara, Kanagawa Japan, 資料番号: SA6000143011, レポート番号: HR-2019-010

平成30年度宇宙輸送シンポジウム（2019年1月17日-18日. 宇宙航空研究開発機構宇宙科学研究所（JAXA)(ISAS)）, 相模原市, 神奈川県, Space Transportation Symposium FY2018 (January 17-18, 2019. Institute of Space and Astronautical Science, Japan Aerospace Exploration Agency (JAXA)(ISAS)), Sagamihara, Kanagawa Japan, 資料番号: SA6000136028, レポート番号: STCP-2018-028

形態: カラー図版あり, Physical characteristics: Original contains color illustrations, 資料番号: PA1710002000

形態: カラー図版あり, Physical characteristics: Original contains color illustrations, 資料番号: AA1530050000, レポート番号: JAXA-RM-15-010

形態: カラー図版あり, Physical characteristics: Original contains color illustrations, 資料番号: AA1530049000, レポート番号: JAXA-RM-15-009

形態: カラー図版あり, Physical characteristics: Original contains color illustrations, 資料番号: AA1530040000, レポート番号: JAXA-RM-15-002

第1回観測ロケットシンポジウム（2018年7月17日-18日. 宇宙航空研究開発機構宇宙科学研究所（JAXA)(ISAS)）, 相模原市, 神奈川県, 1st Sounding Rocket Symposium (July 17-18, 2018. Institute of Space and Astronautical Science, Japan Aerospace Exploration Agency (JAXA)(ISAS)), Sagamihara, Kanagawa Japan, 資料番号: SA6000127017, レポート番号: V-3

第1回ハイブリッドロケットシンポジウム（2018年6月28日-29日. 宇宙航空研究開発機構宇宙科学研究所（JAXA)(ISAS)）, 相模原市, 神奈川県, 1st Hybrid Rocket Symposium (June 28-29, 2018. Institute of Space and Astronautical Science, Japan Aerospace Exploration Agency (JAXA)(ISAS)), Sagamihara, Kanagawa Japan, 資料番号: SA6000126008, レポート番号: HR-2018-007

第1回ハイブリッドロケットシンポジウム（2018年6月28日-29日. 宇宙航空研究開発機構宇宙科学研究所（JAXA)(ISAS)）, 相模原市, 神奈川県, 1st Hybrid Rocket Symposium (June 28-29, 2018. Institute of Space and Astronautical Science, Japan Aerospace Exploration Agency (JAXA)(ISAS)), Sagamihara, Kanagawa Japan, 資料番号: SA6000126011, レポート番号: HR-2018-010

資料番号: PA1510063000

A floating ring seal (FRS) has been employed as a noncontact type seal, which seals in high-pressure liquid oxygen for the rocket engine turbopump. The turbopump, high-speed, high-power turbomachinery, has suffered from rotor vibration problems up to the present time. However, as the dynamic behavior of FRS has rarely been focused on, it is necessary to clarify the rotordynamic (RD) fluid forces of FRS. The objectives of the present study were to evaluate the RD fluid forces of FRS analytically (bulk-flow model) and experimentally, and to elucidate the structural behavior of FRS caused by the whirling motion of the rotor. Evaluation of RD fluid forces was attempted, and development of a program for evaluation of the FRS is now in progress. RD fluid forces of FRS were measured by an experimental apparatus with an active magnetic bearing. These forces had no significant impact on rotordynamic stability. The axial force induced by differential pressure presses the floating-ring (FR, the component of the FRS) against the stationary housing. Because of the increasing friction force of the secondary contact surface, high axial loads increase the radial force required to reposition the FR. Therefore, it is very important to investigate rotordynamic forces as tribological behavior., 形態: カラー図版あり, Physical characteristics: Original contains color illustrations, 資料番号: AA0062043000, レポート番号: JAXA-RM-13-008E

A rocket turbopump, high-speed, high-power turbomachinery, has suffered from various rotor vibration problems up to the present time. Establishment of an integrated design method consisting of turbopump components is eagerly expected to suppress the rotor vibration. We are now studying the design method of optimal rotor system by using multidisciplinary optimization due to information-sharing of turbopump components (pump, bearing, seal and turbine). A quality function deployment (QFD) is employed to visualize of the relation between turbopump components., 形態: カラー図版あり, Physical characteristics: Original contains color illustrations, 資料番号: AA0062042000, レポート番号: JAXA-RM-13-007

形態: カラー図版あり, Physical characteristics: Original contains color illustrations, Translation title: CFD analysis of inner fluid flow in a angular contact ball bearing on cryogenic and high speed condition, 資料番号: AA0062039000, レポート番号: JAXA-RM-13-001

資料番号: PA1410055000

資料番号: PA1410054000

資料番号: PA1410056000

形態: カラー図版あり, Physical characteristics: Original contains color illustrations, 資料番号: AA0061880000, レポート番号: JAXA-RM-12-009

Because rocket turbopump turbine blades have higher loading, there is a possibility of shaft vibration problem due to "Thomas Force". In order to reduce shaft vibrations, it is important to keep "Thomas Force" small. In the previous report, validity of optimization process for the reduction of Thomas Force was confirmed by performing Parameter Design and Multi-Objective Genetic Algorithm (MOGA). In this paper, by increasing the number of objective functions, the results of multi-objective optimization for reduction of Thomas Force and the considering the feasibility of blade structure are discussed. It was found that optimized blade reduced 10% in weight, 30% in Thomas Force, compared from the original blade., 形態: カラー図版あり, Physical characteristics: Original contains color illustrations, 資料番号: AA0065514000, レポート番号: JAXA-RM-12-007

Due to its special specification, rocket turbopump turbine blades have higher loading and its aspect ratio is extremely low. In such a situation, it is difficult to predict turbine efficiency accurately in system design phase of rocket engine. The purpose of the present work is to evaluate the accuracy of existing one dimensional loss model. By using the steady three dimensional CFD analyses, parametric studies against the major design variables such as tip clearance, blade loading, blade aspcet ratio, were carried out. These simulation results were compared with the results that were also obtained by using the existing one dimensional loss models. The results clarified the cause of the reduction of accuracy of one-dimensional prediction of turbine efficiency. The one-dimensional loss model was found to underestimate the loss under the condition of a blade with a low aspect ratio. From comparison between the existing one-dimensional loss models, it was also found that the "Craig & Cox model" could reproduce the tendency for blade loading correctly., 形態: カラー図版あり, Physical characteristics: Original contains color illustrations, 資料番号: AA0065515000, レポート番号: JAXA-RM-12-008

In the present study, numerical analysis carried out around the cyclic flat-plate cascade with a asymmetric slit, so as to examine the suppressing or controlling effect of the slit for cavitation instabilities such as a cavitation oscillation which is similar to cavitation surge, and rotating cavitation. These instabilities cause various problem for the turbomachinery, for example, rotating cavitation causes an asynchronous axial vibration, and cavitation oscillation causes a pulsation of working fluid by resonance phenomenon of the system. Especially, in liquid propellant rocket engine, suppression process for these instabilities bring increase in cost of the launch. Therefore, it is thought that to find effective suppression technique is significant for turbomachinery. In this paper, two types of the flat-plate three blades cascade which have an asymmetric slit on each blade were analyzed, and compare with the result of cascade without slit. As a result, the cavitation oscillation is perfectly suppressed in both of two types cascade with an asymmetric slit. Also, in the one case of them, sub-synchronous rotating cavitation and rotating stall cavitation are suppressed. Furthermore, super-synchronous rotating cavitation which is not observed in single-stage cascade, is detected by arranging an asymmetric slit. These results indicate the possibility of suppressing cavitation instabilities or controlling the type of the cavitation instabilities by the arrangement of the slit. Moreover, the head performance at the almost same cavitation number is equal or slightly increasing by arranging the asymmetric slit.

In this study, numerical investigation of coolant flow across the angular contact ball bearing in a rocket turbopump was performed to evaluate pressure loss of the bearing. The results show that the pressure loss tendencies against the bearing revolution speed were significantly different between the flow directions. It was mainly caused by the flow separation behind the ball and centrifugal force effect of swirl flow made by bearing revolution. Furthermore, we get a simplified pressure loss model of the bearing and it can approximately estimate the difference of the pressure losses between the flow directions., 資料番号: PA1510106000

第57回宇宙科学技術連合講演会（2013年10月9日-11日. 米子コンベンションセンター（BiG SHiP）), 米子市, 鳥取県, Rotor lateral vibration on a rocket turbopump is very serious problem. In order to suppress the rotor instabilities, the newdesign method for a turbopump, so called morphological design method was proposed by JAXA. The design methodconsists of both optimization of the component layout, and optimization of shaft diameter and length of the components.Trial study on morphological design to a hydrogen turbopump for upper stage engine was conducted. Optimizationscenarios and results were presented in this paper., 資料番号: AC1400018000, レポート番号: JSASS-2013-4269

To investigate the relationship of the uneven cavity length and rotordynamic force in a cavitating inducer with three blades, the rotordynamic fluid forces acting on cavitating and whirling inducer were examined by using a rotordynamic test stand with active magnetic bearings. Rotordynamic performances were obtained within a wide range of cavitation numbers (sigma) and whirl(omega)/shaft(Omega) speed ratios included super-synchronous/synchronous/sub-synchronous rotating cavitation. These experimental results indicate that the rotating cavitation strongly affects the fluid reaction forces. The fluid reaction forces act on the inducer as a destabilizing forces at a certan cavitation number and whirl/shaft speed ratio., 形態: カラー図版あり, Physical characteristics: Original contains color illustrations, 資料番号: AA0064454000, レポート番号: JAXA-RM-09-004

Tests were conducted to evaluate the dynamic response of the upper stage turbopump of the H2A. Dynamic response parameters were calculated using the experimental results. It was shown that the dynamic response parameters were proper in comparison with another test results., 資料番号: AA0049500014, レポート番号: JAXA-SP-06-006